WO2014188961A1

WO2014188961A1 - Turbine blade cooling structure

Info

Publication number: WO2014188961A1
Application number: PCT/JP2014/062992
Authority: WO
Inventors: 谷口智紀; 田中良造; 堀内豪; 杉本隆雄; 餝雅英; クステラー・カーステン; ボーン・ディーター; リン・ガーン
Original assignee: 川崎重工業株式会社; ベー・ウント・ベー・アゲマ・ゲーエムベーハー
Priority date: 2013-05-20
Filing date: 2014-05-15
Publication date: 2014-11-27
Also published as: CN105339590A; EP3000972A1; EP3000972A4; JP2014227841A; EP3000972B1; US20160115796A1; JP5567180B1; US10018053B2; CN105339590B; CA2912823A1

Abstract

A structure for cooling a turbine blade (1) from the inside, wherein a cooling medium passage (5) is provided inside the turbine blade (1), and this cooling medium passage (5) has a shape such that portions of multiple substantially cylindrical spaces (S1, S2) extending parallel to each other overlap each other, and a cooling medium supply passage (9) for supplying a cooling medium (CL) to the cooling medium passage is connected to a portion of the cooling medium passage that includes the peripheral wall (15), and in a direction which forms an acute angle with respect to the lengthwise direction of the cooling medium passage.

Description

Turbine blade cooling structure

Related applications

This application claims the priority of Japanese Patent Application No. 2013-105818 filed on May 20, 2013, which is incorporated herein by reference in its entirety.

The present invention relates to a structure for cooling a turbine blade in a turbine of a gas turbine engine from the inside.

The turbine constituting the gas turbine engine is disposed downstream of the combustor and is supplied with high-temperature gas combusted in the combustor, so that it is exposed to high temperatures during operation of the gas turbine engine. Therefore, it is necessary to cool the turbine blades, that is, the stationary blades and the moving blades of the turbine. As a structure for cooling such turbine blades, it is known that a part of air compressed by a compressor is introduced into a cooling passage formed in the blades, and the turbine blades are cooled by using compressed air as a cooling medium. Yes. As an example of such a cooling structure, it has been proposed to form a cooling passage by a circular pipe in a turbine blade and supply a cooling air from one end thereof to generate a swirling flow (for example, Patent Document 1). reference).

US Pat. No. 5,603,606

When a part of compressed air is used for cooling turbine blades, there is no need to introduce a cooling medium from the outside, and there is an advantage that the cooling structure can be simplified. On the other hand, if a large amount of air compressed by the compressor is used for cooling Since this leads to a decrease in engine efficiency, it is necessary to efficiently perform cooling with a minimum amount of air. However, if air is simply allowed to flow through a simple cylindrical space as described above, the air that is the cooling medium only swirls in one direction in the cooling passage, and the temperature distribution in the cooling medium becomes non-uniform and sufficient. The cooling effect cannot be obtained.

Accordingly, an object of the present invention is to provide a cooling system capable of cooling the turbine blades with high efficiency by making the temperature distribution of the cooling medium passing through the cooling passages in the turbine blades uniform in order to solve the above-described problems. To provide a structure.

To achieve the above object, a turbine blade cooling structure according to the present invention is a structure for cooling a turbine blade from the inside, and cooling medium passages provided in the turbine blade extend in parallel to each other. A part of the plurality of substantially cylindrical spaces has a shape overlapping each other, and the cooling medium supply passage for supplying the cooling medium to the cooling medium passage includes the cooling medium in a portion including a peripheral wall of the cooling medium passage. They are connected in a direction that forms an acute angle with the longitudinal direction of the medium passage.

According to this configuration, the cooling medium supplied to the cooling medium passage from the portion including the peripheral wall of the cooling medium passage flows into the plurality of cylindrical spaces, and forms a swirling flow in each cylindrical space. Further, a part of each swirl flow in both cylindrical spaces flows into the other cylindrical space through the overlapping region of both spaces. Thus, when each swirling flow of the cooling medium formed in the adjacent cylindrical space flows into the other, the mixing of the cooling medium is promoted, and the temperature distribution in the cooling medium is made uniform. High cooling efficiency can be obtained. Furthermore, when each swirl flow flows into the other cylindrical space, it collides with the partition sides formed between the cylindrical spaces, thereby providing a high cooling effect due to the impingement effect.

In one embodiment of the present invention, the overlapping length W along a straight line connecting the centers of the two cross-sectional circles of the two adjacent cylindrical spaces is the cross-sectional diameter D1 of one cylindrical space and the other cylindrical space. It is preferable that the two adjacent cylindrical spaces overlap with each other so that 0.05 ≦ W / ((D1 + D2) / 2) ≦ 0.35 is satisfied. By setting the degree of overlap between the two cylindrical spaces in this way, it is possible to ensure that a separate swirl flow is generated in each of the two cylindrical space spaces and that the swirl flows into the adjacent cylindrical space. Can be generated.

In one embodiment of the present invention, a cooling medium supply passage for supplying a cooling medium to the cooling medium passage may be connected to an overlapping region of two cylindrical spaces adjacent to the cooling medium passage. In this case, the cooling medium supply passage is connected to the overlapping region so that the cooling medium supplied from the cooling medium supply passage collides with a partition side formed between the two adjacent cylindrical spaces. It is preferable. According to this configuration, the cooling medium supplied from the cooling medium supply passage collides with the partition side formed between the two spaces, so that the cooling medium is distributed almost evenly in the two cylindrical spaces. Since a swirling flow in the opposite direction with high directivity is formed along the inner wall surface forming the cooling medium, mixing of the cooling medium is further promoted. Also, in the cooling medium supply portion, the cooling medium is collided with the partition side, whereby the cooling of the wall surface is promoted by the impingement effect. Due to these effects, extremely high cooling efficiency can be obtained.

In one embodiment of the present invention, the cooling medium supply passage for supplying the cooling medium passage to the cooling medium passage is a straight line connecting between the centers of both cross-sectional circles of two cylindrical spaces adjacent to each other in the cooling medium passage. You may connect to the side part on the opposite side to the overlapping area | region of cylindrical shape space. According to this structure, the flexible design according to the shape of the site | part of the turbine blade to which the said cooling structure is applied is attained.

Any combination of at least two configurations disclosed in the claims and / or the specification and / or drawings is included in the present invention. In particular, any combination of two or more of each claim in the claims is included in the present invention.

The present invention will be more clearly understood from the following description of preferred embodiments with reference to the accompanying drawings. However, the embodiments and drawings are for illustration and description only and should not be used to define the scope of the present invention. The scope of the invention is defined by the appended claims. In the accompanying drawings, the same reference numerals in a plurality of drawings indicate the same or corresponding parts.
It is a perspective view showing an example of a turbine blade to which a cooling structure concerning a 1st embodiment of the present invention is applied. It is sectional drawing which shows typically the cooling structure of the turbine blade of FIG. It is a perspective view which shows the shape of the cooling medium channel | path of the cooling structure of FIG. It is sectional drawing which shows the shape of the cooling-medium channel | path of the cooling structure of FIG. It is a cross-sectional view of the front end portion of the turbine blade of FIG. It is sectional drawing which shows typically the effect | action of the cooling structure of FIG. It is sectional drawing which shows typically the cooling-medium supply channel | path of the cooling structure of FIG. It is sectional drawing which shows typically the example of the cooling structure of the turbine blade which concerns on 2nd Embodiment of this invention. It is sectional drawing which shows typically the example of the cooling structure of the turbine blade which concerns on 3rd Embodiment of this invention.

Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. FIG. 1 is a perspective view showing a moving blade 1 which is a turbine blade of a turbine of a gas turbine engine to which a turbine blade cooling structure according to a first embodiment of the present invention is applied. The turbine rotor blade 1 has a platform 2 connected to the outer peripheral portion of the turbine disk, so that a large number of turbine blades 1 are implanted in the circumferential direction to form a turbine. The turbine rotor blade 1 is exposed to the hot gas G flowing in the direction of the arrow supplied from the combustor. In the following description, the upstream side (left side in FIG. 1) along the flow direction of the hot gas G is referred to as the front, and the downstream side (right side in FIG. 1) is referred to as the rear. In the present embodiment, the cooling structure is applied to the inside of the front end portion 1 a that is particularly high in the turbine rotor blade 1.

As shown in FIG. 2, a first coolant passage 5 extending along the radial direction of the turbine (the vertical direction in the figure) is formed in the front end 1a of the turbine rotor blade 1. Compressed air from the compressor used as the cooling medium CL is introduced into the turbine rotor blade 1 through a cooling medium introduction passage 6 formed in the turbine disk 3. A part of the cooling medium CL introduced into the turbine rotor blade 1 is supplied to the first cooling medium passage 5. The remaining part of the cooling medium CL introduced into the turbine rotor blade 1 is supplied to the second cooling medium passage 7 for cooling the rear portion 1b of the turbine rotor blade 1. By passing the cooling medium CL through the cooling

medium passages

5 and 7, the turbine rotor blade 1 is cooled from the inside. The cooling medium CL supplied to the first cooling medium passage 5 is discharged from the discharge hole 8 communicating with the outside of the turbine rotor blade 1.

As shown in FIG. 3, the first cooling medium passage 5 has a shape in which a plurality of (two in this example) substantially cylindrical cylindrical spaces S1 and S2 extending in parallel with each other overlap each other. Yes. That is, as shown in FIG. 4, the cross section of the first cooling medium passage 5 has a shape in which two circles (hereinafter referred to as cross-sectional circles) C1 and C2 are partially overlapped. In this specification, “substantially cylindrical” means a cylindrical shape having a circular cross-sectional shape, or a cylindrical shape having an elliptical shape in which the ratio of the short axis length to the long axis length is 0.5 or more. means. In the illustrated example, the diameter D1 of one cross-sectional circle C1 and the diameter D2 of the other cross-sectional circle C2 are set to the same value, but both the diameters D1, D2 may be set to different values.

The degree of overlap between the two adjacent cylindrical spaces S1 and S2 is closer to each other than the circumscribed state of the cross-sectional circles C1 and C2, and the inscribed state (when both diameters D1 and D2 are equal). The cross section circles C1 and C2 are not particularly limited as long as they are separated from each other. However, as a preferable overlapping degree for separating the cooling medium CL more effectively in the first cooling medium passage 5, the centers O1, O2 of the cross-sectional circles C1, C2 of the two adjacent cylindrical spaces S1, S2 are used. The overlap length W along the straight line L between the two is 0.05 ≦ W / ((D1 + D2) / 2) ≦ 0 with respect to the diameter D1 of one cross-sectional circle C1 and the diameter D2 of the other cross-sectional circle C2. .35, preferably 0.10 ≦ W / ((D1 + D2) / 2) ≦ 0.30, and W / ((D1 + D2) / 2) = 0. More preferably, it is 20. In the following description, a direction along a straight line L connecting the centers O1 and O2 of both cross-sectional circles C1 and C2 of two adjacent cylindrical spaces S1 and S2 is simply referred to as a width direction X.

By setting the degree of overlap between the two cylindrical spaces S1 and S2 in this way, as will be described in detail later with reference to FIG. 6, separate swirl flows R1 and R2 are generated in the cylindrical spaces S1 and S2, respectively. It is possible to reliably generate a phenomenon in which the swirl flows R1 and R2 flow into adjacent cylindrical spaces.

As shown in FIG. 6, the cooling medium supply passage 9 that supplies the cooling medium CL to the first cooling medium passage 5 is connected to the overlapping region M of the two adjacent cylindrical spaces S <b> 1 and S <b> 2 of the first cooling medium passage 5. Has been. In particular, the cooling medium supply is performed so that the cooling medium CL supplied from the cooling medium supply path 9 to the first cooling medium path 5 collides with the partition side 11 formed between two adjacent cylindrical spaces S1 and S2. The passage 9 is preferably connected to the overlap region M. More specifically, the cooling medium supply passage 9 is perpendicular to the width direction X in a cross-sectional view with respect to the overlapping region M between the cylindrical spaces S1 and S2, and the center of the passage is substantially at the opposing partition side 11. Connected in a matching arrangement. Here, as shown in FIG. 3, the partition side 11 partitions between the adjacent cylindrical space S1, S2, that is, the peripheral wall forming the cylindrical space S1 and the peripheral wall forming the cylindrical space S2. It is a side formed in a portion that extends in the longitudinal direction of the first cooling medium passage 5.

As shown in FIG. 5, the width direction X substantially matches the thickness direction of the turbine rotor blade 1, for example. The cooling medium CL supplied into the first cooling medium flow path 5 is sprayed to the outside from a plurality of injection holes 13 formed in the front end portion 1a, and the blade surface of the front end portion 1a is film-cooled.

Further, as shown in FIG. 7, the cooling medium supply passage 9 is connected to a portion including the peripheral wall 15 of the first cooling medium passage 5 in a direction that forms an acute angle with respect to the longitudinal direction of the first cooling medium passage 5. Yes. In the illustrated example, the cooling medium supply passage 9 is connected to a corner portion 19 formed between the peripheral wall 15 and the bottom wall 17 at the upstream end portion of the first cooling medium passage 5. The angle α formed by the longitudinal direction of the cooling medium supply passage 9 and the first cooling medium passage 5 is not particularly limited as long as it is a value larger than 0 ° and smaller than 90 °, but the cooling medium CL is surely the first cooling medium. In order to form a swirling flow in the passage 5, the angle α is preferably in the range of 15 ° ≦ α ≦ 60 °, and more preferably in the range of 30 ° ≦ α ≦ 45 °.

According to the cooling structure including the first cooling medium passage 5 configured as described above, the first cooling medium passage 5 is connected to the first cooling medium passage 5 via the cooling medium supply passage 9 as shown in FIG. After the cooling medium CL supplied from the portion including the peripheral wall flows into the cylindrical spaces S1 and S2, the swirl flows R1 and R2 are formed in the cylindrical spaces S1 and S2, respectively. Further, in the process of passing through the first cooling medium passage 5 as the swirl flow R1, R2, a part of the swirl flow R1 flowing on the outer diameter side via the overlapping region M of the spaces S1, S2 is a cylinder. A part flowing from the shape space S1 to S2 and flowing on the outer diameter side of the swirl flow R2 flows from the cylindrical space S2 to S1. In this way, when the swirl flows R1 and R2 in the cylindrical spaces S1 and S2 flow into the other cylindrical spaces S2 and S1, the mixing of the cooling medium CL is promoted, and the temperature distribution in the cooling medium CL is increased. Since it is made uniform, high cooling efficiency can be obtained. Furthermore, when each swirl | vortex flow R1, R2 collides with the partition side 11 formed between cylindrical shape space S1, S2, the high cooling effect by an impingement effect is brought about.

In particular, in the illustrated example, since the cooling medium supply passage 9 is connected to the overlapping region M of the adjacent cylindrical spaces S1 and S2, the cooling medium CL is transferred from the cooling medium supply passage 9 to the first cooling medium passage 5. Even when it flows in, it collides with the partition side 11 formed between the two spaces S1, S2. By this partition side 11, the cooling medium CL is distributed almost evenly in the two cylindrical spaces S1, S2, and swirl flows R1, swirling in opposite directions along the inner wall surfaces forming the cylindrical spaces S1, S2, respectively. Since R2 is formed, mixing in the overlapping region M is further promoted. In the supply portion of the cooling medium CL, the cooling of the wall surface is promoted by the impingement effect by causing the cooling medium CL to collide with the partition side 11. Due to these effects, extremely high cooling efficiency can be obtained.

The form of the cooling structure is not limited to the example described above, and the cooling medium passage provided in the turbine blade has a shape in which a plurality of substantially cylindrical spaces extending in parallel with each other overlap each other. And the cooling medium supply passage is connected to the portion including the peripheral wall of the cooling medium passage in a direction that forms an acute angle with respect to the longitudinal direction of the cooling medium passage, Mixing of the cooling medium CL is promoted when they flow into each other, and the effect that the temperature distribution in the cooling medium CL is made uniform is obtained.

For example, as a second embodiment of the present invention, the coolant supply passage 9 is opposite to the overlapping region M of the cylindrical space on the straight line L of the first coolant passage 5 as shown in FIG. It may be connected to one of the

side portions

5a and 5a. Alternatively, as shown in FIG. 8B, two cooling medium supply passages 9 may be provided and connected to both sides of the first cooling medium passage 5. When the cooling medium supply passage 9 is thus connected to the side portion 5a of the cooling medium passage 5, the supply direction of the cooling medium CL by the cooling medium supply passage 9 in the cross-sectional view of the first cooling medium passage 5 is the cross-sectional circle C1. , C2 is preferably set so as to be in the tangential direction. In the second embodiment, the configuration other than that specifically described above is such that the cooling medium supply passage 9 is in a portion including the peripheral wall 15 of the first cooling medium passage 5 with respect to the longitudinal direction of the first cooling medium passage 5. The configuration is the same as that of the first embodiment including the configuration connected in the direction that forms an acute angle.

Further, as the third embodiment of the present invention, the number of cylindrical spaces forming the first cooling medium passage 5 is not limited to two, and for example, as shown in FIG. 9, three cylindrical spaces S1, S2, S3 May be arranged in this order, and adjacent cylindrical spaces S1 and S2, and S2 and S3 may have shapes that overlap each other. In this case, as shown in FIG. 9 (a), the shape of the first cooling medium passage 5 is formed by arranging three cylindrical spaces S1 to S3 in a substantially straight line (that is, each of the sectional circles C1, C2, and C3). The centers O1, O2, and O3 may be in the same straight line shape. However, according to the shape of the turbine blade portion to which this cooling structure is applied, as shown in FIG. The width direction X1 of S2 and the width direction X2 of the cylindrical spaces S2, S3 may not be parallel (that is, the centers O1, O2, O3 of the cross-sectional circles C1, C2, C3 are not collinear). . The same applies when the number of cylindrical spaces is four or more.

In the third embodiment, the configuration other than that specifically described above is such that the cooling medium supply passage 9 is in a portion including the peripheral wall 15 of the first cooling medium passage 5 with respect to the longitudinal direction of the first cooling medium passage 5. The configuration is the same as that of the first embodiment including the configuration connected in the direction that forms an acute angle.

The cooling structure exemplified as the first to third embodiments is applied not only to the front end portion 1a of the turbine rotor blade 1, but also to the second cooling medium passage 7 of the rear portion 1b instead of or in addition to this. Also good. In any of the embodiments, the cooling medium CL is not limited to the compressed air from the compressor, and other gases or liquids generally used as a cooling medium may be used. Furthermore, the cooling structure according to the present invention can be applied to a turbine stationary blade in addition to the turbine rotor blade 1 as a turbine blade of a gas turbine.

As described above, the preferred embodiments of the present invention have been described with reference to the drawings, but various additions, modifications, or deletions can be made without departing from the spirit of the present invention. Therefore, such a thing is also included in the scope of the present invention.

1 Turbine blade (turbine blade)
5 First cooling medium passage (cooling medium passage)
9 Cooling medium supply passage 15 Perimeter wall CL of cooling medium passage Cooling medium C1, C2, C3 Cross-sectional circle M Overlapping region O1, O2, O3 Center of cross-sectional circle S1, S2, S3 Cylindrical space

Claims

A structure for cooling turbine blades from the inside,
The cooling medium passage provided in the turbine blade has a shape in which a part of a plurality of substantially cylindrical spaces extending in parallel with each other overlap each other,
A cooling medium supply passage for supplying a cooling medium to the cooling medium passage is connected to a portion including a peripheral wall of the cooling medium passage in a direction that forms an acute angle with respect to a longitudinal direction of the cooling medium passage.
Turbine blade cooling structure.
2. The cooling structure according to claim 1, wherein an overlap length W along a straight line connecting the centers of both cross-sectional circles of two adjacent cylindrical spaces has a cross-sectional diameter D <b> 1 of one cylindrical space and the other cylinder. A turbine blade cooling structure in which the two adjacent cylindrical spaces overlap so that 0.05 ≦ W / ((D1 + D2) / 2) ≦ 0.35 with respect to the cross-sectional diameter D2 of the shape space.
3. The cooling structure according to claim 1, wherein the cooling medium supply passage is connected to an overlapping region of two cylindrical spaces adjacent to the cooling medium passage.
The cooling structure according to claim 3, wherein the cooling medium supplied from the cooling medium supply path collides with a partition side formed between the two adjacent cylindrical spaces. Is a cooling structure of a turbine blade connected to the overlap region.
3. The cooling structure according to claim 1, wherein the cooling medium supply passage overlaps the cylindrical space on a straight line connecting the centers of both cross-sectional circles of two cylindrical spaces adjacent to the cooling medium passage. Turbine blade cooling structure connected to the side opposite the region.